公开(公告)号：US20160144957A1

公开(公告)日：2016-05-26

申请号：US14554892

申请日：2014-11-26

Applicant: XCraft Enterprises, LLC

Inventor： Jerry Daniel Claridge ,  Charles Fischer Manning

IPC: B64C29/02 ,  B64C27/08 ,  B64C27/26

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108

Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.

Abstract translation: 本公开通常涉及包括固定翼飞行能力的高速垂直起飞和着陆（VTOL）飞机。 高速垂直起降飞机可以包括至少两个推力产生的转子，其位于主机翼上与飞行器的纵向轴线等距的转子，以及至少两个推力产生的转子，其在垂直翼上与飞行器的纵向轴线等距离。 转子可以由电动机驱动。 然而，可以使用其它动力源，例如燃烧或混合发动机。 通过调整转子的速度和/或桨距，飞机可以从垂直飞行配置转换到水平飞行配置并返回。

公开(公告)号：US20160031564A1

公开(公告)日：2016-02-04

申请号：US14882254

申请日：2015-10-13

Applicant: Flight of the Century, Inc.

Inventor： William M. YATES

IPC: B64D33/00 ,  B64C39/02

CPC classification number: B64D3/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/187 ,  B64D33/00 ,  B64D39/00

Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, and method of deploying and retrieving secondary aircrafts.

Abstract translation: 电动飞机，包括飞行中可充电电动飞机，以及运行电动飞机的方法，包括为飞行中的电动飞机充电的方法，以及部署和检索二次飞机的方法。

公开(公告)号：US20160016675A1

公开(公告)日：2016-01-21

申请号：US14698770

申请日：2015-04-28

Applicant: AeroVironment, Inc.

Inventor： John Peter Zwaan ,  Robert James Johnston ,  Cris James Cornell ,  Philip Martin Finn ,  Glenn Arnold Blevins ,  David Wayne Ganzer

IPC: B64F1/02 ,  B64C39/02 ,  B63B17/00

CPC classification number: B64F1/02 ,  B63B17/00 ,  B63B35/52 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/025

Abstract: Systems, devices, and methods for impacting, by a small unmanned aerial vehicle (SUAV), a net having at least three sides; and converting the kinetic energy of the SUAV into at least one of: elastic potential energy of one or more tensioned elastic cords connected to at least one corner of the net, gravitational potential energy of a frame member connected to at least one corner of the net, rotational kinetic energy of the frame member connected to at least one corner of the net, and elastic potential energy of the frame member connected to at least one corner of the net.

Abstract translation: 通过小型无人机（SUAV）的影响系统，设备和方法，至少有三面网; 以及将所述SUAV的动能转换为与所述网的至少一个角连接的一个或多个张紧弹性绳的弹性势能，连接到所述网的至少一个角的框架构件的重力势能 连接到网的至少一个角的框架构件的旋转动能以及连接到网的至少一个角的框架构件的弹性势能。

公开(公告)号：US20160016652A1

公开(公告)日：2016-01-21

申请号：US14734864

申请日：2015-06-09

Applicant: Ronald M. Barrett ,  Robert B. Honea ,  Richard B. Bramlette

Inventor： Ronald M. Barrett ,  Robert B. Honea ,  Richard B. Bramlette

IPC: B64C3/00 ,  A63H27/00 ,  B64C15/02 ,  B64C11/00 ,  B64C25/06 ,  B64C9/00

CPC classification number: A63H27/12 ,  A63H27/02 ,  A63H33/003 ,  B64C25/06 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2203/00 ,  B64D27/02

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

Abstract translation: 能够从悬停到线性飞行的可转换飞行的飞行器包括具有纵向轴线的主体，多个前翼，多个后翼，至少一个马达以及由至少一个驱动的至少三个空气动力推进器 发动机。 每个前翼延伸一个前翼平面。 每个后翼从后翼平面延伸。 空气动力学推进器纵向安装在多个前翼和多个后翼之间。

公开(公告)号：US20150329218A1

公开(公告)日：2015-11-19

申请号：US14518348

申请日：2014-10-20

Applicant: Advanced Aerospace Technologies, Inc.

Inventor： William R. McDonnell ,  Charles H. Baker

IPC: B64F1/10 ,  B64C39/02 ,  B64D3/00

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将UAV（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US09169014B2

公开(公告)日：2015-10-27

申请号：US13569360

申请日：2012-08-08

Applicant: Andrew Charles Elson ,  Peter Davidson

Inventor： Andrew Charles Elson ,  Peter Davidson

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle at an altitude of at least 13,000 m, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种在至少13000米的高度上发射供电的无人驾驶飞行器的方法，该方法包括通过将空载承载装置从基本上地平面的位置附近提升到升高的高度，使车辆 当车辆相对于承载件的速度基本上为零时，车辆离开载体，然后车辆随着其高度减小到能够防止任何进一步下降并且可以开始独立的持续飞行的速度。

公开(公告)号：US20150232178A1

公开(公告)日：2015-08-20

申请号：US14378604

申请日：2013-02-13

Applicant: Johannes REITER

Inventor： Johannes Reiter

IPC: B64C29/00 ,  B64C37/00 ,  B64C3/38

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

公开(公告)号：US09010678B1

公开(公告)日：2015-04-21

申请号：US13786299

申请日：2013-03-05

Applicant: The Boeing Company

Inventor： Nathan Hiller

IPC: B60F5/02

CPC classification number: B60F5/02 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/205 ,  B64C2201/206

Abstract: A vehicle which is adaptable for both flight and water travel includes: a body; a wing, a stabilizer, or a first propelling member; and at least one attachment member. The body is configured to fly through air and to move through water. The at least one attachment member attaches the wing, the stabilizer, or the first propelling member to the body while the body is in flight. The at least one attachment member detaches at least a portion of the wing, at least a portion of the stabilizer, or at least a portion of the first propelling member from the body when the body is in the water.

Abstract translation: 适用于飞行和水上旅行的车辆包括：身体; 翼，稳定器或第一推进构件; 和至少一个附接构件。 身体被配置为飞过空气并移动通过水。 当身体飞行时，至少一个附接构件将翼，稳定器或第一推进构件附接到身体。 当身体在水中时，至少一个附接构件将至少一部分翼，至少一部分稳定器，或至少一部分第一推进构件与身体分开。

公开(公告)号：US20140312165A1

公开(公告)日：2014-10-23

申请号：US14217387

申请日：2014-03-17

Applicant: Armen Mkrtchyan

Inventor： Armen Mkrtchyan

IPC: B64D47/08 ,  B64C39/02

CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  G06K9/00657 ,  G06K9/2018

Abstract: A hand-launched unmanned aerial vehicle (UAV) to determine various characteristics of ground surfaces. The UAV includes a lightweight and robust body/wing assembly, and is equipped with multiple consumer-grade digital cameras that are synchronized to acquire high-resolution images in different spectra. In one example, one camera acquires a visible spectrum image of the ground over which the UAV is flown, and another camera is modified to include one or more filters to acquire a similar near-infrared image. A camera mount/holder system facilitates acquisition of high-quality images without impacting the UAV's flight characteristics, as well as easy coupling and decoupling of the cameras to the UAV and safeguarding of the cameras upon landing. An intuitive user interface allows modestly trained individuals to operate the UAV and understand and use collected data, and image processing algorithms derive useful information regarding crop health and/or soil characteristics from the acquired images.

Abstract translation: 一种手动无人机（UAV）来确定地面各种特性。 无人机包括一个轻量级和坚固的身体/翼组件，并配备了多个消费级数码相机，同步以获取不同光谱的高分辨率图像。 在一个示例中，一个摄像机获取飞行无人机的地面的可见光谱图像，并且修改另一摄像机以包括一个或多个滤波器以获取类似的近红外图像。 相机安装/支架系统便于获取高质量的图像，而不会影响UAV的飞行特性，以及轻松耦合和解耦相机到UAV，并在着陆时保护相机。 直观的用户界面允许受过训练的人员操作无人机，了解和使用收集的数据，图像处理算法从所获取的图像中得到有关作物健康和/或土壤特性的有用信息。

公开(公告)号：US20140217229A1

公开(公告)日：2014-08-07

申请号：US14347375

申请日：2012-09-14

Applicant: Keen Ian Chan

Inventor： Keen Ian Chan

IPC: B64C29/02 ,  A63H27/00 ,  B64C13/24 ,  B64F5/00 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C13/24 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  G05D1/0669 ,  Y10T29/49826

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.

Abstract translation: 能够进行垂直和水平飞行模式的无人飞行器（UAV），组装无人机的方法和用于组装无人机的一套零件。 无人机包括翼结构，其包括细长的相等的第一和第二翼; 支撑结构，包括联接到所述机翼结构的中间位置并且在与所述机翼结构垂直的相反方向上延伸的第一和第二部分; 以及四个螺旋桨，每个螺旋桨安装到第一和第二翼中的相应一个以及第一和第二部分，用于在垂直和水平飞行模式期间为无人机提供动力。